TURBINE AIRFOIL WITH LOCAL WALL THICKNESS CONTROL

A turbine airfoil for a gas turbine engine includes: an outer peripheral wall having an external surface (58), the outer peripheral wall enclosing an interior space and including a concave pressure sidewall (50) and a convex suction sidewall (52) joined together at a leading edge (54) and at a trail...

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Bibliographische Detailangaben
Hauptverfasser:	BAUER, RANDALL CHARLES, STERGEMILLER, MARK EDWARD, MOLTER, STEVE MARK, CEGLIO, CHRISTOPHER MICHAEL
Format:	Patent
Sprache:	eng ; fre
Schlagworte:	BLASTING ENGINE PLANTS IN GENERAL HEATING INDEXING SCHEME FOR ASPECTS RELATING TONON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES ORJET-PROPULSION PLANTS INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUSSUBCLASSES OF CLASSES F01-F04 LIGHTING MACHINES OR ENGINES IN GENERAL MECHANICAL ENGINEERING NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAMTURBINES STEAM ENGINES WEAPONS
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Beschreibung
Zusammenfassung:	A turbine airfoil for a gas turbine engine includes: an outer peripheral wall having an external surface (58), the outer peripheral wall enclosing an interior space and including a concave pressure sidewall (50) and a convex suction sidewall (52) joined together at a leading edge (54) and at a trailing edge (56); wherein the outer peripheral wall has a varying wall thickness which incorporates a locally-thickened wall portion (Z1, Z2, Z3); and a film cooling hole (74) having a shaped diffuser exit passing through the outer peripheral wall within the locally-thickened wall portion (Z1, Z2, Z3).